Aeroplane radiator



Dec. 26, 1922.

P. L. PARSONS.

AEROPLANE RADIATOR.

FILED MAR. 8, I921.

Patented Dec. 2%, 1922 narrate stares rarest orator...

PETER L. PARSONS, 01F CRISTOBAL, PANAMA, CANAL ZONE.-

AEBOPLANE aamaroa.

Application filed March 8,

' To all whom it may concern Be it known that 1, PETER L. PARSONS, a citizen of the United States residing at Cristobal, in the count-y of (lristobal and State of Panama, have invented new and useful Improvements in Aeroplane Radiators, of which the following is a specification.

This invention relates to improvements in radiators, and has particular reference to an aeroplane radiator adapted to be installed beneath the fuselage of an aeroplane.

One object of this invention is to redure I the weight of the aeroplane construction by eliminating the nose radiator and in its place utilizing the landing gear construction.

A still further object of this invention is to provide an apparatus of the character described, which serves to produce a low center of.gravity, thereby tending to increase'the lateral stability of the aeroplane to which it is attached.

Another object of this invention is to provide an apparatus of the character described, which is located in the slip stream of the propeller, where it .will be exposed to a larger air circulating surface and thereby more readily cooled.

A still further object of this invention is to provide an apparatus of the character described, which is simple and etiicient in construction, thereby reducing the eight of the machine, compactin the arrangement of its parts, inexpensive to manufacture, and highly serviceable.

:Other objects and advantagesof vthislinvention will be apparent during the course of the following description.

In the construction of aeroplanes, it has been found that the ordinary landing gear is only dead resistance'when the machine of the machine maybe stream lined and thus reduce to a minimum the air resistance on the fuselage, I have devised the following novel type of radiator construction. 1

In the accompanying drawings forming a part of this specification and in which like numerals are employed. to designate like parts throughout the same,

Figurel is a front elevationof my ap- 'of illustration is shown a preferred embodiment of my invention, the numeral 4 designates an aeroplane body or fuselage, which has, disposed beneath the same a tubular axle 5 sealed adjacent its opposite extremities and terminating in hub members 6, which have mounted thereon the usual landing gear wheels 7, preferably of the spring wheel type. The axle forms part of the circulating systemof my apparatus and has associated therewith and disposed adjacent the hub members 6 a pair of substantially U shaped members. Each U shaped member consists of front and rear tubular arms, 8 and 8, respectively, an intermediate collar portion 9 adapted to encircle and to be soldered to the axle 5 or otherwise rigidly secured thereto, and a cross tube 10 preferably made of steel, although copper may also be employed.

Disposed within and radiating from the front arms 8, are the extremities of a pair of forward tubular struts 11, which, have mounted on their respective opposite extremities front Ts 12. These Ts have in tegrall formed therewith fittings 13 adapted to e suitably secured on the front underside of the body or fuselage of the aeroplane.

Likewise disposed within the rear arms 8 are the extremities of a pair of rear tubular struts 14 which have carried on their opposite extremities rear Ts 15, which are also provided with integrally formed fittings 16- adapted to be suitably secured to the underside of the fuselage or body of the aeroplane.

Encircling the hollow axle 5 in close proximity to the pair of U shaped arms are collars 17, which have integrally formed therewith elbows 18. Adapted to connect the elbows 18 andthe Ts 12, are a pair of tubes 19, which not only form part of my circulating system, but also act as cross bars. Connecting the rear Ts 15' is an, angularly bent tubular cross piece 20 which has disposedthereon an inlet pipe 21 for the purthat hot water coming from the top of the water jacket of the engine, will pass through the tubular cross piece 20, then through the rear struts 14, through the cross tubes 10,

i then upwardly through the front tubular struts 11, next. through the cross'pieces 19 to the interior of the axle 5, and thenupwardly throughthe exit or outlet pipe 22 to the bottom of the water jacket of the engine. This circulation of the water is indicated by the arrows, as shown to advantage in Figures 1 and 2, and it will be obvious that water passing through the series of tubes and pipes will besubjected at all'times. to the cooling eflect' of the atmosphere. I

In the construction of my apparatus, steel is the preferred material which is adapted to be galvanized interiorly 'and exteriorly. In order that a compact structure may be furnished, I propose to weld or braze together the various elements forming my apparatus. As shown to advantage in detail in Figure 3, the struts are elliptical in form.- This construction is preferably employed in the whole apparatus in order that a desired stream line effect will be had with a consequent reduction of resistance of the apparatus during the flight of the machine. While my apparatus is shown attached to an aeroplane, it is to be understood that it is not to be limited toan aeroplane, but that it mayalso be applied to flying machines of various types.

It is also to be understood that the 'form' of my invention, herewith shown and described, is to be taken as a preferred example of the same, and that various changes in the shape, size and arrangementof parts may be resorted to Without departing from the spirit of the invention, 01; the scope ofthe. subjoined claims. 7

Having thus described my invention, I claim a 1. In an apparatus of the character described, the combination with the body of a flying machine, of a tubular landing axle positioned beneath said body and terminating struts of stream-line formconnected to said axle and-the body of said machine, tubular cross pieces of stream line form connected to said axle and said front tubular struts, and inlet and outlet means connected to said rear struts and said axle for the purpose specified.

2. In an apparatus of the character described, the combination with the b0dy,of a flyingmachine, of a tubular axle positioned beneath said body and terminating in hub members, wheels mounted on and adapted to support said axle, front and rear'tubular struts having their lower extremities connected to said axle and their upper extremities provided withfittings adapted to be secured to the body of said machine, cross pieces connected to said axle and said front tubular struts, an angular tubular cross piece connected to said'rear tubular struts, and inlet means connected to said cross pieces and said axle for delivering fluid to be cooled to said series of tubular elements, and an exit pipesecured to said axle for returnin the cooled water to the interior of the b0 y of the flying machine.

3. In an apparatus of the character desaid hubs, tubular struts secured to each leg of said U-shaped members, said struts extending upwardly, one of said struts from' each of said U-shaped members extending forwardly and one of said struts from each of said U-shaped members extending 'rearwardly, said struts being connected to said body, a tiibular cross-piece connecting said rearwardly extending struts, an inlet pipe extending into said cross-piece and adapted to conduct heated water thereto, tubular pipes secured to said forwardly extending struts at their free ends, said pipes crossing and being connected to said tubular portions of said axle at opposite ends thereof, and an exit pipe secured to said axle near its center portion. I

In testimony whereof I aflix my signature.

PETER L. PARSONS. 

